68052 Federal Register / Vol. 77, No. 221 / Thursday, November 15, 2012 / Rules and Regulations 

been repaired as specified in an Airbus 

structural repair manual or repair approval 

sheet as of the effective date of this AD: 

Before the accumulation of 10,000 total flight 

cycles since first flight of the airplane, or 

within 600 flight cycles after the effective 

date of this AD, whichever occurs later, 

perform a high frequency eddy current 

(HFEC) inspection for cracking of the 

crossbeam fuselage frame stations FR 22/23 

and FR 61/62, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of 

this AD. Repeat the inspection thereafter at 

intervals not to exceed 600 flight cycles until 

the modification specified in paragraph (i) of 

this AD has been done. 

(i) Airbus Mandatory Service Bulletin 

A300–53–0390, dated January 15, 2010 (for 

Model A300 series airplanes). 

(ii) Airbus Mandatory Service Bulletin 

A310–53–2134, dated January 15, 2010 (for 

Model A310 series airplanes). 

(iii) Airbus Mandatory Service Bulletin 

A300–53–6168, dated January 15, 2010 (for 

Model A300–600 series airplanes). 

(2) For airplanes on which the crossbeams 

at FR 22/23 and FR 61/62 have been repaired 

as specified in an Airbus structural repair 

manual or repair approval sheet as of the 

effective date of this AD: Before the 

accumulation of 10,000 total flight cycles 

since first flight of the airplane, or within 600 

flight cycles after the effective date of this 

AD, whichever occurs later, repair in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

(h) Corrective Action 

If any crack is found during any inspection 

required by paragraph (g) of this AD: Before 

further flight, repair any crack using a 

method approved by the Manager, 

International Branch, ANM–116; or EASA (or 

its delegated agent). 

(i) Optional Terminating Action 

Modifying the crossbeam fuselage frame 

stations FR 22/23 and FR 61/62, including 

doing rotating probe inspections for cracks of 

fastener holes, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraph (i)(1), (i)(2), or (i)(3) of this AD, 

and repairing any crack using a method 

approved by the Manager, International 

Branch, ANM–116; or EASA (or its delegated 

agent); terminates the repetitive inspections 

required by paragraph (g)(1) of this AD. 

(1) Airbus Service Bulletin A300–53–0389, 

Revision 02, dated April 27, 2011 (for Model 

A300 series airplanes). 

(2) Airbus Service Bulletin A310–53–2133, 

Revision 02, dated April 27, 2011 (for Model 

A310 series airplanes). 

(3) Airbus Service Bulletin A300–53–6166, 

Revision 01, dated May 21, 2010 (for Model 

A300–600 series airplanes). 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

227–1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(k) Related Information 

Refer to EASA Airworthiness Directive 

2011–0086, dated May 12, 2011; and the 

service information identified in paragraphs 

(k)(1), (k)(2), (k)(3), (k)(4), (k)(5), and (k)(6) of 

this AD, for related information. 

(1) Airbus Mandatory Service Bulletin 

A300–53–0390, dated January 15, 2010. 

(2) Airbus Mandatory Service Bulletin 

A300–53–6168, dated January 15, 2010. 

(3) Airbus Mandatory Service Bulletin 

A310–53–2134, dated January 15, 2010. 

(4) Airbus Service Bulletin A300–53–0389, 

Revision 02, dated April 27, 2011. 

(5) Airbus Service Bulletin A300–53–6166, 

Revision 01, dated May 21, 2010. 

(6) Airbus Service Bulletin A310–53–2133, 

Revision 02, dated April 27, 2011. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Airbus Mandatory Service Bulletin 

A300–53–0390, dated January 15, 2010. 

(ii) Airbus Mandatory Service Bulletin 

A300–53–6168, dated January 15, 2010. 

(iii) Airbus Mandatory Service Bulletin 

A310–53–2134, dated January 15, 2010. 

(iv) Airbus Service Bulletin A300–53– 

0389, Revision 02, dated April 27, 2011. 

(v) Airbus Service Bulletin A300–53–6166, 

Revision 01, dated May 21, 2010. 

(vi) Airbus Service Bulletin A310–53– 

2133, Revision 02, dated April 27, 2011. 

(3) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(4) You may review copies of the 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on October 

24, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–27055 Filed 11–14–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0643; Directorate 

Identifier 2011–NM–190–AD; Amendment 

39–17241; AD 2012–22–05] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain Fokker Services B.V. Model F.28 

Mark 0070 and 0100 airplanes. That AD 

currently requires performing a detailed 

visual inspection for cracks of the 

pistons on the main landing gear (MLG), 

and replacing the affected pistons if 

necessary. This new AD also requires 

modifying the MLG by installing a 

piston containing a certain part number, 

and revising the airplane maintenance 

program. This AD was prompted by a 

new modification developed to 

safeguard the integrity of the MLG 

assembly and improve surface 

protection of the affected area of the 

MLG piston. We are issuing this AD to 

prevent MLG failure, possibly resulting 

in loss of control of the airplane during 

the landing roll-out. 

DATES: This AD becomes effective 

December 20, 2012. 


wreier-aviles on DSK5TPTVN1PROD with 
Federal Register / Vol. 77, No. 221 / Thursday, November 15, 2012 / Rules and Regulations 68053 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 20, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of March 22, 2011 (76 FR 

8618, February 15, 2011). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

425–227–1137; fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 21, 2012 (77 FR 37337), 

and proposed to supersede AD 2011– 

04–01, Amendment 39–16601 (76 FR 

8618, February 15, 2011). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The 

Mandatory Continuing Airworthiness 

Information (MCAI) states: 

During a normal walk around check on a 

F28 Mark 0100 aeroplane, a large crack was 

discovered in the lower portion of the right 

(RH) MLG piston. The affected MLG unit had 

accumulated 7,909 flight cycles (FC) at the 

time of detection. The piston was sent to 

Goodrich, the landing gear manufacturer, for 

detailed investigation, which revealed that 

the crack had been initiated by corrosion 

pits. The extent of the corrosion indicates 

that the initial crack existed for a substantial 

period before a high loading event caused the 

crack to grow further by ductile overload. 

This condition, if not detected and 

corrected, could lead to MLG failure during 

the landing roll-out, possibly resulting in 

damage to the aeroplane and injury to 

occupants. 

To address this potential unsafe condition, 

EASA [European Aviation Safety Agency] 

issued AD 2009–0221 [which corresponds 

with FAA AD 2011–04–01, Amendment 39– 

16601 (76 FR 8618, February 15, 2011)] to 

require a one-time detailed visual inspection 

of the MLG pistons, the replacement of any 

MLG pistons on which cracks are detected, 

and the reporting of all findings to the 

aeroplane TC [type certificate] holder. No 

cracks were reported as a result of this 

inspection. 

Subsequently, a repetitive inspection was 

introduced in the Airworthiness Limitations 

Section (Fokker Services report SE–623 Issue 

8) in Appendix 1 of the Maintenance Review 

Board (MRB) document to safeguard the 

integrity of the MLG assembly, pending the 

accomplishment of a terminating action. 

Goodrich issued Service Bulletin (SB) 

41000–32–29 to introduce an improved 

surface protection (nickel plate) of the 

affected area of the MLG piston P/N [part 

number] 41141–3 and re-identification as P/ 

N 41141–5, which is considered as a 

terminating action for the repetitive 

inspections. 

For the reasons described above, this 

[EASA] AD requires repetitive visual 

inspections of the P/N 41141–3 MLG piston 

for cracks and, depending on findings, 

replacement or modification of the MLG 

piston. This [EASA] AD also requires 

modification of the affected MLG by 

installing a piston P/N 41141–5. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Change Made to This AD 

We have revised paragraphs (k), (l), 

and (n), of this final rule to clarify the 

document citation of Fokker Report SE– 

623 to meet the Office of Federal 

Register’s guidelines for materials 

incorporated by reference. There is no 

change to the requirements specified in 

those paragraphs. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 37337, June 21, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed—except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

37337, June 21, 2012) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 37337, 

June 21, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

about 2 products of U.S. registry. 

The actions that are required by AD 

2011–04–01, Amendment 39–16601 (76 

FR 8618, February 15, 2011), and 

retained in this AD take about 3 workhours per product, at an average labor 

rate of $85 per work-hour. Based on 

these figures, the estimated cost of the 

currently required actions is $255 per 

product. 

We estimate that it will take about 24 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of this AD to the U.S. 

operators to be $4,080, or $2,040 per 

product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 


wreier-aviles on DSK5TPTVN1PROD with 
68054 Federal Register / Vol. 77, No. 221 / Thursday, November 15, 2012 / Rules and Regulations 

contains the NPRM (77 FR 37337, June 

21, 2012), the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2011–04–01, Amendment 39–16601 (76 

FR 8618, February 15, 2011), and adding 

the following new AD: 

2012–22–05 Fokker Services B.V.: 

Amendment 39–17241. Docket No. 

FAA–2012–0643; Directorate Identifier 

2011–NM–190–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective December 20, 2012. 

(b) Affected ADs 

This AD supersedes AD 2011–04–01, 

Amendment 39–16601 (76 FR 8618, February 

15, 2011). 

(c) Applicability 

(1) This AD applies to Fokker Services B.V. 

Model F.28 Mark 0070 and 0100 airplanes, 

certificated in any category, all serial 

numbers, equipped with Goodrich (formerly 

Menasco, Colt Industries) main landing gear 

(MLG) units, part numbers (P/N) 41050–7, 

41050–8, 41050–9, 41050–10, 41050–11, 

41050–12, 41050–13, 41050–14, 41050–15, 

41050–16, 41060–1, 41060–2, 41060–3, 

41060–4, 41060–5, or 41060–6. 

(2) This AD requires revisions to certain 

operator maintenance documents to include 

new actions (e.g., inspections). Compliance 

with these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these actions, the 

operator may not be able to accomplish the 

actions described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance (AMOC) 

according to paragraph (m)(1) of this AD. The 

request should include a description of 

changes to the required inspections that will 

ensure the continued operational safety of 

the airplane. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32: Landing Gear. 

(e) Reason 

This AD was prompted by a new 

modification developed to safeguard the 

integrity of the MLG assembly and improve 

surface protection of the affected area of the 

MLG piston. We are issuing this AD to 

prevent MLG failure, possibly resulting in 

loss of control of the airplane during the 

landing roll-out. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Initial Inspection 

This paragraph restates the initial 

inspection required by paragraph (g) of AD 

2011–04–01, Amendment 39–16601 (76 FR 

8618, February 15, 2011). Within 30 days 

after March 22, 2011 (the effective date of AD 

2011–04–01), do a detailed visual inspection 

for cracks of the MLG pistons, in accordance 

with the Accomplishment Instructions of 

Fokker Service Bulletin SBF100–32–158, 

dated October 2, 2009. 

(h) Retained Replacement 

This paragraph restates the replacement 

required by paragraph (h) of AD 2011–04–01, 

Amendment 39–16601 (76 FR 8618, February 

15, 2011). If any cracked MLG piston is found 

during the inspection required by paragraph 

(g) of this AD, before further flight, replace 

the affected piston with a serviceable part, in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–32–158, dated October 2, 2009. 

(i) New Modification 

Within 120 months, or during a scheduled 

overhaul of the MLG, whichever occurs first 

after the effective date of this AD: Modify the 

MLG by installing a piston containing P/N 

41141–5, in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–32–161, dated April 

7, 2011. Re-installation of a MLG piston that 

has been modified and re-identified as P/N 

41141–5, in accordance with the 

Accomplishment Instructions of Goodrich 

Service Bulletin 41000–32–29, dated 

November 10, 2010, is an optional method of 

compliance for the requirements specified in 

paragraph (i) of this AD. It is acceptable to 

operate an airplane with one MLG having a 

P/N 41141–5 piston installed, and the other 

MLG having a P/N 41141–3 piston installed, 

provided all MLG P/N 41141–3 are replaced 

within the compliance times specified in 

paragraph (i) of this AD. 

(j) New Parts Installation Prohibition 

After 120 months after the effective date of 

this AD: No person may install a MLG piston, 

P/N 41141–3, or a MLG unit equipped with 

a MLG piston P/N 41141–3, on any airplane. 

(k) New Revision of the Airplane 

Maintenance Program 

Within 2 months after the effective date of 

this AD: Revise the airplane maintenance 

program by incorporating Task 321100–01– 

16, Inspection of MLG Piston, and associated 

thresholds and intervals described in Fokker 

Report, SE–623, Fokker 70/100 

Airworthiness Limitation Items and Safe Life 

Items, Issue 8, dated December 20, 2010. The 

initial compliance time for Task 321100–01– 

16 is within 2 months after the effective date 

of this AD. 

(l) No Alternative Actions or Intervals 

After accomplishing the revisions required 

by paragraph (k) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used other than those specified in Fokker 

Report, SE–623, Fokker 70/100 

Airworthiness Limitation Items and Safe Life 

Items, Issue 8, dated December 20, 2010, 

unless the actions and intervals are approved 

as an AMOC in accordance with the 

procedures specified in paragraph (m)(1) of 

this AD. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone 425–227–1137; fax 425–227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(n) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2011–0159, 

dated August 26, 2011, and the service 

information specified in paragraphs 

(n)(1)through (n)(4) of this AD, for related 

information. 

(1) Fokker Service Bulletin SBF100–32– 

158, dated October 2, 2009. 

(2) Fokker Service Bulletin SBF100–32– 

161, dated April 7, 2011. 


wreier-aviles on DSK5TPTVN1PROD with 
Federal Register / Vol. 77, No. 221 / Thursday, November 15, 2012 / Rules and Regulations 68055 

(3) Fokker Report, SE–623, Fokker 70/100 

Airworthiness Limitation Items and Safe Life 

Items, Issue 8, dated December 20, 2010. 

(4) Goodrich Service Bulletin 41000–32– 

29, dated November 10, 2010. 

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on December 20, 2012. 

(i) Fokker Service Bulletin SBF100–32– 

161, dated April 7, 2011. 

(ii) Fokker Report, SE–623, Fokker 70/100 

Airworthiness Limitation Items and Safe Life 

Items, Issue 8, dated December 20, 2010. 

(iii) Goodrich Service Bulletin 41000–32– 

29, dated November 10, 2010. 

(4) The following service information was 

approved for IBR on March 22, 2011 (76 FR 

8618, February 15, 2011). 

(i) Fokker Service Bulletin SBF100–32– 

158, dated October 2, 2009. 

(ii) Reserved. 

(5) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 231, 2150 

AE Nieuw-Vennep, the Netherlands; 

telephone +31 (0)252–627–350; fax +31 

(0)252–627–211; email 

technicalservices.fokkerservices@stork.com; 

Internet http://www.myfokkerfleet.com. For 

Goodrich Corporation service information 

identified in this AD, contact Goodrich, 1400 

South Service Road, West Oakville, L6L 5Y7, 

Ontario, Canada, telephone +1–905–827– 

7777; fax +1–905–825–1583; Internet http:// 

www.goodrich.com/TechPubs. 

(6) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on October 

24, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–26781 Filed 11–14–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0530; Directorate 

Identifier 2011–SW–075–AD; Amendment 

39–17247; AD 2012–22–11] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Bell 

Helicopter Textron (BHT) Model 412, 

412EP, and 412CF helicopters. This AD 

requires a repetitive inspection of the 

collective lever for a crack, and if there 

is a crack, before further flight, replacing 

the collective lever with an airworthy 

collective lever. This AD was prompted 

by a reported failure of a collective 

lever. The actions are intended to detect 

a crack in the collective lever, which 

could lead to failure of the collective 

lever and subsequent loss of control of 

the helicopter. 

DATES: This AD is effective December 

20, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of December 20, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Bell 

Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, Texas 76101; telephone 

(817) 280–3391; fax (817) 280–6466; or 

at http://www.bellcustomer.com/files/. 

You may review a copy of the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

Examining the AD Docket: You may 

examine the AD docket on the Internet 

at http://www.regulations.gov or in 

person at the Docket Operations Office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Martin Crane, Aerospace Engineer, 

Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5170; email 

martin.r.crane@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 22, 2012, at 77 FR 30232, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

include an AD that would apply to 

certain serial-numbered BHT Model 

412, 412EP, and 412CF helicopters with 

a collective lever, part number (P/N) 

412–010–408–101. That NPRM 

proposed to require within 25 hours 

time-in-service (TIS) or 30 days, 

whichever occurs first, and thereafter at 

intervals not to exceed 100 hours TIS, 

cleaning the collective lever and 

inspecting it for cracks with a 10X or 

higher power magnifying glass. If there 

is a crack in the collective lever paint 

finish, the NPRM proposed to require 

removing the collective lever from the 

swashplate and performing a fluorescent 

penetrant inspection, and if there is a 

crack in the collective lever, before 

further flight, replacing the collective 

lever with an airworthy collective lever. 

The proposed requirements were 

intended to detect a crack in the 

collective lever, which could lead to 

failure of the collective lever and 

subsequent loss of control of the 

helicopter. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (77 FR 30232, May 22, 2012). 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Related Service Information 

We reviewed Bell Helicopter Alert 

Service Bulletin (ASB) No. 412–11–148 

and ASB No. 412CF–11–47, both 

Revision A, and both dated December 

12, 2011, which describe procedures for 

repetitively inspecting the collective 

lever with a magnifying glass and a 

strong light source and, if necessary, a 

fluorescent penetrant inspection. If 

there is a crack, the ASBs require 

replacing the collective lever. 


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